-
公开(公告)号：EP4417790A1
公开(公告)日：2024-08-21
申请号：EP24158469.7
申请日：2024-02-19
申请人： RTX Corporation
IPC分类号： F01D5/18
摘要： A turbine blade (74) for a gas turbine engine, including: an airfoil (80), the having a leading edge (82), a pressure side (84), a suction side (86) and a trailing edge (88); a plurality of internal cooling cavities including a leading edge cavity (90), a leading edge feed passage (92), pressure side cooling passages (94), suction side cooling passages (96) and main body cavities (98); the leading edge cavity (90) extending towards the suction side (86); a first crossover row of cooling passages (100) providing fluid communication between the leading edge cavity (90) and the leading edge feed passage (92); and a second crossover row of cooling passages (102) providing fluid communication between the leading edge cavity (90) and the leading edge feed passage (92), a centerline (144) of the first crossover row of cooling passages (100) is located closer to the pressure side (84) than a centerline (136) of the second crossover row of cooling passages (102) and the centerline (136) of the second crossover row of cooling passages (102) is located closer to the suction side (86) than the centerline (144) of the first crossover row of cooling passages (100), and wherein the second crossover row of cooling passages (102) are radially staggered relative to the first crossover row of cooling passages (100).
-
2.发明公开
公开(公告)号：EP4311915A1
公开(公告)日：2024-01-31
申请号：EP23175879.8
申请日：2023-05-28
申请人： RTX Corporation
摘要： A method for vane classification includes scanning, using a structured light scanner (220), a vane (230) for a turbine engine (20) to capture three-dimensional (3D) data about the vane (230). The method further includes generating a point cloud from the 3D data about the vane (230). The method further includes connecting, using a processing system (210), points of the point cloud to generate a mesh surface. The method further includes determining, using the processing system (210), an airflow for an airfoil of the vane (230) based at least in part on the mesh surface. The method further includes constructing the turbine engine based at least in part on the airflow for the airfoil of the vane (230) without reference to an adjacent airfoil of the vane (230).
-
公开(公告)号：EP4249727A3
公开(公告)日：2024-01-10
申请号：EP23163580.6
申请日：2023-03-22
申请人： RTX Corporation
摘要： An inspection device (305) is disclosed herein. In various embodiments, the inspection system device comprises: a support structure (302) ; a motor (404); a shaft (308) operably coupled to the motor (404), the shaft (308) extending from a first side of the support structure (302) to a second side of the support structure (302), the shaft (308) configured to couple to a bladed rotor; and a scanner (310) moveably coupled to the support structure (302), the scanner (310) configured to generate a three-dimensional model for the bladed rotor.
-
4.发明公开
公开(公告)号：EP4365419A2
公开(公告)日：2024-05-08
申请号：EP24165958.0
申请日：2021-04-23
申请人： RTX Corporation
IPC分类号： F01D25/24
CPC分类号： F01D25/246 , F05D2300/60320130101 , Y02T50/60
摘要： An assembly (60) for a gas turbine engine (20) according to an example of the present disclosure includes, among other things, a composite gas turbine engine component (62) including a first flange (70) extending radially from a main body (68) at a junction (82) having an arcuate profile. An adapter ring (188) includes a mate face (177) dimensioned to follow a contour (183) of the junction (82) such that the junction (82) sits on the mate face (177). A method of assembly for a gas turbine engine is also disclosed.
-
公开(公告)号：EP4442961A2
公开(公告)日：2024-10-09
申请号：EP24196021.0
申请日：2018-06-21
申请人： RTX Corporation
IPC分类号： F01D5/14
CPC分类号： F05D2230/21120130101 , F05D2300/60820130101 , F01D5/147 , F01D5/186 , F05D2260/20420130101 , Y02T50/60
摘要： A turbine engine component (100) includes a wall (150) extending from a leading edge (170) to a trailing edge (180). The wall (150) includes a hot side surface (211) facing a gaspath when the component (100) is in an installed state, and a cold side surface (212) opposite the hot side surface (211). At least one minicore cooling circuit (290) is disposed between the hot side surface (211) and the cold side surface (212) within the wall (150). At least one cooling fluid inlet (214) connects the minicore cooling circuit (290) to a coolant source (213). At least one film cooling hole (217) connects the minicore cooling circuit (290) to the hot side surface (211). The minicore cooling circuit (290) includes an edge plenum (216) having a thickness (220) normal to the hot side surface (211) that is larger than a thickness (221) of the majority of the minicore cooling circuit (290) normal to the hot side surface (211). The edge plenum (216) is a portion of the at least one minicore cooling circuit (290) most proximate to one of the leading edge (170) and the trailing edge (180).
-
公开(公告)号：EP4249845A3
公开(公告)日：2024-01-10
申请号：EP23158302.2
申请日：2023-02-23
申请人： RTX Corporation
IPC分类号： G01B3/14
摘要： A method (200) is disclosed herein. In various embodiments, the method (200) comprises: coupling a sheath (700) to an airfoil (601) of an integrally bladed rotor (100), the sheath (700) comprising a plurality of apertures (731, 732, 733, 734, 735) disposed therein; and coupling a plurality of locators (1000) to the integrally bladed rotor (100), each locator (1000) in the plurality of locators (100) disposed through a corresponding aperture (731, 732, 733, 734, 735) in the plurality of apertures (731, 732, 733, 734, 735).
-
公开(公告)号：EP4454782A2
公开(公告)日：2024-10-30
申请号：EP24200906.6
申请日：2019-11-11
申请人： RTX Corporation
IPC分类号： B22C9/04
摘要： A gas turbine engine article (60, 102) includes a cooling passage network (76, 176, 276) embedded in an article wall (68, 168) between inner and outer portions (68a, 168a, 68b, 168b) of the article wall. The network has an inlet orifice (78) through the inner portion to receive cooling air from a cavity (74, 174), a sub-passage region (80) that includes an array of pedestals (82, 182, 282), and at least one outlet orifice (81a) through the outer portion. The array of pedestals includes first pedestals (83, 83.1, 83.2, 183.1, 183.2, 283.1, 283.2) arranged in a first row (85, 85.1, 85.2, 185.1, 185.2, 285.1, 285.2) and second pedestals (84, 84.1, 84.2, 184.1, 184.2, 284.1, 284.2) arranged in a second, adjacent row (86, 86.1, 86.2, 186.1, 186.2, 286.1, 286.2). The first pedestals and the second pedestals define inter-row sub-passages (87, 187, 287) therebetween. Each of the inter-row sub-passages has an inlet mouth (88, 188, 288), an outlet mouth (89, 189, 289), and a compound channel (90, 190, 290) connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length (91, 191, 291) over which the inter-row sub-passage has a constant cross-section (91a, 191a, 291a) and a second channel length (92, 192, 292) over which the inter-row sub-passage has a non-constant cross-section (92a, 192a, 292a).
-
8.发明公开
公开(公告)号：EP4365419A3
公开(公告)日：2024-07-31
申请号：EP24165958.0
申请日：2021-04-23
申请人： RTX Corporation
IPC分类号： F01D25/24
CPC分类号： F01D25/246 , F05D2300/60320130101 , Y02T50/60 , F01D25/243
摘要： An assembly (60) for a gas turbine engine (20) according to an example of the present disclosure includes, among other things, a composite gas turbine engine component (62) including a first flange (70) extending radially from a main body (68) at a junction (82) having an arcuate profile. An adapter ring (188) includes a mate face (177) dimensioned to follow a contour (183) of the junction (82) such that the junction (82) sits on the mate face (177). A method of assembly for a gas turbine engine is also disclosed.
-
公开(公告)号：EP4276281A1
公开(公告)日：2023-11-15
申请号：EP23169584.2
申请日：2023-04-24
申请人： RTX Corporation
摘要： A method comprises: flowing a potted component in a liquid state over a tip (214) of an airfoil (210), the tip (214) of the airfoil (210) having a coating (220) disposed thereon, the coating (220) comprising a metal plating (221) and a plurality of protrusions (222), each protrusion in the plurality of protrusions (222) extending from the metal plating (221); allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip (214) of the airfoil (210).
-
-
-
-
-
-
-
-
搜索结果
9 条记录 (耗时 0.012 秒)
